Stored energy initiator type of fuze

ABSTRACT

This is a nose fuze construction. A firing pin projects forwardly through an actuator in position to be directly actuated by high impact forces. The actuator is associated with a prestressed firing spring to store mechanical energy and is associated with an inertia member which senses soft or indirect impact and shifts position, releasing the actuator and firing spring, so that the firing pin is driven to perform the firing operation. Both the firing pin and the inertia member are locked in position by centrifugal-force-responsive weights which move radially outwardly to unlock the firing pin and inertia member. A second spring causes the forward nose portion of the firing pin to assume an exposed position when these weights are in their unlocking position.

nite tates ate t [1 1 [111 3,824,929 Webb [45] Jul 23, 1974 STORED ENERGY INITIATOR TYPE OF Primary Examiner-Samuel W. Engle FUZE [76] Inventor: George Webb, 420 5. 22nd St.,

Richmond, Ind. 47374 [22] Filed: Dec. 15, 1965 21] Appl. NO.Z 514,148

[52] US. Cl. 102/74, 102/79 [51] Int. Cl. F42c 1/00 [58] Field of Search 102/73, 73 U, 76, 79, 80,

[56] References Cited UNITED STATES PATENTS 1,292,505 l/l919 Newell 102/73 2,701,527 2/1955 Granath et al 102/80 X 2,709,962 6/1955 Funk, Jr. et al. i. 102/78 3,264,995 8/1966 Libby et a1 102/73 X Attorney, Agent, or Firm-Charles M. Hogan [57] ABSTRACT This is a nose fuze construction. A firing pin projects forwardly through an actuator in position to be directly actuated by high impact forces. The actuator is associated with a prestressed firing spring to store mechanical energy and is associated with an inertia member which senses soft or indirect impact and shifts position, releasing the actuator and firing spring, so that the firing pin is driven to perform the firing operation. Both the firing pin and the inertia member are locked in position by centrifugal-force-responsive weights which move radially outwardly to unlock the firing pin and inertia member, A second spring causes the forward nose portion of the firing pin to assume an exposed position when these weights are in their unlocking position.

5 Claims, 2 Drawing Figures PArEmEnmzslm GEOR INVENTOR GE WEBB I 7%; AK

ATTORNEYS 1 STORED ENERGY INITIATOR TYPE OF FUZE The present invention relates to mechanical fuzes of the type adapted to be installed in the nose of a missile or the like.

The principle object of the invention is to provide a For a better understanding of the invention, together with other and further objects, advantages, and capabilities thereof, reference is made to the following description of the accompanying drawings, in which:

FIG. 1 is an axial sectional view of the front part of a missile body, including a duly installed nose fuze in accordance with the invention; and

FIG. 2 is a sectional view, taken along section line 22 of FIG. 1 and looking in the direction of the arrows.

The fuze here illustrated is shown as installed in a conventional missile having a generally cylindrical body and frontal formations appropriate for the reception of a fuze. Fitted to the extreme front of the body is a conventional aluminum ogive 1 l, and the missile body is formed with an enlarged cylindrical housing portion 12 for the fuze. The parts of the fuze are positioned within a suitable aluminum cap member 13. A generally circular principal support member 14, formed with a central aperture, is positioned as shown within the rear portion of the cover 13. The support member is formed with a forwardly extending integral boss 15, which in turn is formed with radially extending locking channels registering with similar radially extending locking channels in a brass inertia ring member 16. The ring member 16 is formed with an internal annular flange 17.

A steel firing pin is centrally disposed within the cover 13 for slidable axial movement therein. This firing pin is formed with a rearwardly extending pointed working portion 18 projecting through the central aperture in the support 14, with a spool-like intermediate portion 19 having locking formations thereon, and with a forwardly extending nose portion 20. The firing pin is proportioned to be driven rearwardly by direct impact force to perform a detonating function on solid impact between the nose of the projectile and a tangible object.

Centrifugal-force-responsive locking weights or pins 21 and 22, which may be of steel, project through the locking channels in the inertia ring and the support member into the locking formations 19 on the firing pin and restrain the firing pin against any sliding or axial movement. These locking pins or weights are retained in place by a steel locking spring 23. These locking weights constitute centrifugal-force-responsive means which normally locks the inertia ring and the firing pin against axial movement but responds to centrifugal forces to unlock said pin and inertia ring.

Disposed forwardly of the spool-like portion 19 of the firing pin and formed with a transverse passageway therethrough to accept the nose portion of the firing pin is an aluminum actuator member 24. This actuator member, in the position shown, forwardly urges the central portion of, and therefore prestresses for energy storage purposes, a steel firing spring 25. The actuator and firing spring constitute energy-storage means adapted to be restrained to store mechanical energy and to be released to drive the firing pin rearwardly. The firing spring 25 comprises two three-leaf portions, both suitably secured to actuator 24 and exerting bias against cap 13. The inertia ring is provided with a suitable annular brass cover 26.

Restraining means is interposed between the inertia member and the actuator, which restraining means is effective when the inertia member is locked but is ineffective when the inertia member is unlocked. This means comprises locking balls 29 and 30.

Considering now a cycle of operation, it will be assumed that the missile rotates in the counter-clockwise direction (FIG. 2), whereupon centrifugal forces move the spring-restrained locking pins 21 and 22 outwardly. Positioned rearwardly of the spool portion 19 of the firingpin is a creep spring 27, which moves the pin forwardly. The locking weights continue to move radially outwardly to free the inertia ring 16, which is only slightly restrained by its retaining spring 31. Now, this fuze may include a suitable delay arming mechanism including a sliding or rotatable part (not shown), rearward of plate 28, for carrying a detonator and for positioning the detonator in line with the firing pin in response to spin forces. Such delay arming mechanisms are well known in the art. The projecting portion 18 of the firing pin may be used to lock the movable detonator-carrying member ina safe position until a critical spin is attained.

Returning now to the radially outward movement of the locking weights 21 and 22, the firing pin is urged forwardly and the missile is now assumed to be in normal flight, ready to be firedon impact.

On solid direct impact of crush-type magnitude, the nose portion of firing pin 20 is impacted, and the firing pin is driven sharply rearwardly to perform its detonating function. On the other hand, if the crash and resultant crush-up of the ogive is insufficient to fire the fuze, as may be the case if soft snow is impacted, then the cycle of events is as follows: deceleration of the projectile causes the inertia ring 16 to move forwardly, freeing the locking balls 29 and 30 located between flange 17 and suitable detent formations on the actuator 24, whereupon the prestressed firing spring 25 drives the actuator rearwardly. The drive of the actuator rearwardly causes the firing pin also to be driven rearwardly to perform its pointdetonating function.

Therefore it will be seen that the mixer is detonated either by direct impact or by reason of the mechanical energy stored in the prestressed spring 25 and the actuator.

Materials herein mentioned are illustrative, not restrictive.

Thus it will be seen that the invention comprises, in a fuze of the type adapted to be installed in the nose of a missile or the like, a combination of elements arranged to assure firing of the missile either on solid direct impact or soft landing, comprising: a support member 14 formed with a central aperture and radially extending channels; an axially slidably mounted firing pin comprising a rearwardly extending working portion 18, an enlarged intermediate portion 19 formed with locking formations thereon and a forwardly extending nose portion 20; an inertia ring 16 formed with a plurality of radially extending locking channels in registry with the channels of the support member; a plurality of springrestrained lock members 21-22 normally engaging said locking formations to lock said inertia ring and to restrain said firing pin against axial movement, but mounted and arranged to move radially outwardly in response to centrifugal forces to unlock the firing pin and the inertia ring from said support member; an actuator member 24 mounted forwardly of the intermediate portion of the firing pin and formed with a central passageway through which the nose portion of the firing pin projects, said actuator having detent formations; locking balls 29-30 between the inertia ring and the actuator member for normally restraining the actuator member against axial movement; a creep spring 27 positioned rearwardly of the intermediate firing pin portion and adapted to advance the firing pin forwardly on removal from the firing pin of the restraint imposed by the lock members; a firing spring 25 positioned forwardly of the actuator and prestrained to store energy; whereby direct impact forces move the firing pin rearwardly and soft landing forces decelerate the missile so that the locking ring moves forwardly, unlocking the lockingballs from the actuator and permitting the firing spring to drive the actuator and the firing pin rearwardly to perform the requisite detonating function.

Note is made of the fact that a graze impact will not relock the firing pin, once armed, because as spring 27 pushes the firing pin forwardly, the locking surfaces on section 19 of the firing pin are no longer in line with weights 21, 22, and the rear enlarged portion of 19 prevents the weights 21, 22 from re-engaging with the firing pin,

While there has been shown and described what is at present considered to be the preferred embodiment of the invention, it will be understood by those skilled in the art that various changes and modifications may be made therein without departing from the true scope of the invention as defined by the appended claims.

I claim:

1. In a fuze of the type adapted to be installed in the nose of a missile or the like, a combination of elements arranged to assure firing of the missile either on solid direct impact orsoft landing comprising:

a support member formed with a central aperture and radially extending channels,

an axially slidably mounted firing pin comprising a rearwardly extending working portion,

an enlarged intermediate portion formed ing formations thereon,

and a forwardly extending nose portion,

an inertia ring formed with a plurality of radially extending locking channels in registry with the channels of the support member,

a plurality of spring restrained lock members normally engaging said locking formations to lock said inertia ring and to restrain said firing pin against axial movement but mounted and arranged to move radially outwardly in response to centrifugal forces to unlock the firing pin and the inertia ring from said support member,

an actuator member mounted forwardly of the intermediate portion of the firing pin and formed with a central passageway through which the nose portion of the firing pin projects,

said actuator having detent formations,

locking balls between the inertia ring and the detent formations of the actuator member for normally restraining the actuator member against axial movement,

with locka creep spring positioned rearwardly of the intermediate firing pin portion and adapted to advance the firing pin forwardly on removal from the firing pin of the restraint imposed by the lock members,

a firing spring positioned forwardly of the actuator and pre-strained to store energy,

whereby direct impact forces move the firing pin rearwardly and soft landing forces decelerate the missile whereby the locking ring moves forwardly, unlocking the locking balls from the actuator and permitting the firing spring to drive the actuator and the firing pin rearwardly to perform the requisite detonating function.

2. In a fuze of the type to be installed in the nose of a missile or the like, the combination of:

a firing pin proportioned to be driven rearwardly by direct impact force to perform a detonating function on solid impact between the nose of the missile and a tangible object;

the firing pin being formed with a rearwardly extending working portion and an enlarged intermediate portion having locking surfaces and a forwardly extending nose portion;

energy storage means comprising an actuator member and a firing spring and adapted to be restrained to store mechanical energy and to be released to drive said firing pin rearwardly;

the actuator member being formed slidably to receive said nose portion;

an inertia member responsive to soft impact for releasing the energy-storage means so that said mechanical energy is utilized in driving the firing pin rearwardly;

centrifugal-force-responsive means comprising lock members which normally engage said locking surfaces to lock said inertia member and said firing pin against axial movement but respond to centrifugal forces to unlock said firing pin and said inertia member; and

restraining means interposed between the inertia member and the actuator, which restraining means is effective when the inertia member is locked but is ineffective when the inertia member is in unlocked condition and moves forwardly in response to impact.

3. In a fuze the combination in accordance with claim 2 and including a creep spring to force the firing pin forwardly so that its enlarged intermediate portion touches the actuator when the locking members release the firing pin.

4. In a fuze the combination in accordance with claim 3 in which the restraining means comprises locking balls and in which the restraint imposed on the actuator becomes ineffective when the inertia member is released by said locking members.

5. In a fuze of the type to be installed in the nose of a missile or the like, the combination of:

a firing pin proportioned to be driven rearwardly by impact force exerted directly on the firing pin to perform a detonating function on solid impact between the nose of the missile and a tangible object;

the firing pin having a forwardly extending nose portion;

energy storage means comprising an actuator member and a prestressed firing spring and adapted to be restrained to store mechanical energy and to be released to drive said firing pin rearwardly;

the actuator member having a forward face and being formed slidably to receive said nose portion and said nose portion extending forwardly of said actuator member in position to be directly impacted when the firing pin is in unlocked condition;

an inertia member responsive to soft impact for releasing the energy-storage means so that said mechanical energy is utilized in driving the firing pin rearwardly in the event of soft impact force not exerted directly on the firing pin;

centrifugal-force-responsive means members which lock said inertia member and said firing pin against axial movement but respond to centrifugal forces to unlock said firing pin and said inertia member;

spring means for urging said firing pin forwardly when it is in unlocked condition; and

restraining means interposed between the inertia member and the actuator, which restraining means is effective when the inertia member is locked but is ineffective when the inertia member is unlocked and moves forwardly in response to impact. 

1. In a fuze of the type adapted to be installed in the nose of a missile or the like, a combination of elements arranged to assure firing of the missile either on solid direct impact or soft landing comprising: a support member formed with a central aperture and radially extending channels, an axially slidably mounted firing pin comprising a rearwardly extending working portion, an enlarged intermediate portion formed with locking formations thereon, and a forwardly extending nose portion, an inertia ring formed with a plurality of radially extending locking channels in registry with the channels of the support member, a plurality of spring restrained lock members normally engaging said locking formations to lock said inertia ring and to restrain said firing pin against axial movement but mounted and arranged to move radially outwardly in response to centrifugal forces to unlock the firing pin and the inertia ring from said support member, an actuator member mounted forwardly of the intermediate portion of the firing pin and formed with a central passageway through which the nose portion of the firing pin projects, said actuator having detent formations, locking balls between the inertia ring and the detent formations of the actuator member for normally restraining the actuator member against axial movement, a creep spring positioned rearwardly of the intermediate firing pin portion and adapted to advance the firing pin forwardly on removal from the firing pin of the restraint imposed by the lock members, a firing spring positioned forwardly of the actuator and prestrained to store energy, whereby direct impact forces move the firing pin rearwardly and soft landing forces decelerate the missile whereby the locking ring moves forwardly, unlocking the locking balls from the actuator and permitting the firing spring to drive the actuator and the firing pin rearwardly to perform the requisite detonating function.
 2. In a fuze of the type to be installed in the nose of a missile or the like, the combiNation of: a firing pin proportioned to be driven rearwardly by direct impact force to perform a detonating function on solid impact between the nose of the missile and a tangible object; the firing pin being formed with a rearwardly extending working portion and an enlarged intermediate portion having locking surfaces and a forwardly extending nose portion; energy storage means comprising an actuator member and a firing spring and adapted to be restrained to store mechanical energy and to be released to drive said firing pin rearwardly; the actuator member being formed slidably to receive said nose portion; an inertia member responsive to soft impact for releasing the energy-storage means so that said mechanical energy is utilized in driving the firing pin rearwardly; centrifugal-force-responsive means comprising lock members which normally engage said locking surfaces to lock said inertia member and said firing pin against axial movement but respond to centrifugal forces to unlock said firing pin and said inertia member; and restraining means interposed between the inertia member and the actuator, which restraining means is effective when the inertia member is locked but is ineffective when the inertia member is in unlocked condition and moves forwardly in response to impact.
 3. In a fuze the combination in accordance with claim 2 and including a creep spring to force the firing pin forwardly so that its enlarged intermediate portion touches the actuator when the locking members release the firing pin.
 4. In a fuze the combination in accordance with claim 3 in which the restraining means comprises locking balls and in which the restraint imposed on the actuator becomes ineffective when the inertia member is released by said locking members.
 5. In a fuze of the type to be installed in the nose of a missile or the like, the combination of: a firing pin proportioned to be driven rearwardly by impact force exerted directly on the firing pin to perform a detonating function on solid impact between the nose of the missile and a tangible object; the firing pin having a forwardly extending nose portion; energy storage means comprising an actuator member and a prestressed firing spring and adapted to be restrained to store mechanical energy and to be released to drive said firing pin rearwardly; the actuator member having a forward face and being formed slidably to receive said nose portion and said nose portion extending forwardly of said actuator member in position to be directly impacted when the firing pin is in unlocked condition; an inertia member responsive to soft impact for releasing the energy-storage means so that said mechanical energy is utilized in driving the firing pin rearwardly in the event of soft impact force not exerted directly on the firing pin; centrifugal-force-responsive means members which lock said inertia member and said firing pin against axial movement but respond to centrifugal forces to unlock said firing pin and said inertia member; spring means for urging said firing pin forwardly when it is in unlocked condition; and restraining means interposed between the inertia member and the actuator, which restraining means is effective when the inertia member is locked but is ineffective when the inertia member is unlocked and moves forwardly in response to impact. 